A method of treating a ceramic matrix composite article, including selecting an article having a ceramic composition formed by a process comprising an initial melt infiltration at an initial temperature with an initial infiltration material, whereby said article has at least one treatable feature. A portion of the ceramic composite is removed from a region abutting the treatable feature to form a treatment region. A treatment material including a reinforcing fiber is positioned in the treatment region and densified by a first melt infiltration with a first infiltration material including silicon. The first melt infiltration is performed at a first temperature lower than the initial infiltration temperature of the initial melt infiltration.

The present invention discloses a turbine engine with at least a high pressure and a low pressure turbine section comprising a casing and at least one turbine blade rotatably mounted within the casing wherein at least part of the inner surface of the casing is covered with shrouds as abradables to provide clearance control between the inner surface and the tip of the at least one blade and wherein the tip of the blade is coated G with a hard PVD coating, characterized in that the shroud material of at least the high pressure and/or the low pressure section comprises a porous ceramic based material and the hard PVD coating on the tip of the blade essentially consists of a droplet free nitride coating.

An article has a cavity defined by an inner surface, the cavity having a size such that a largest sphere placeable in the cavity has a diameter of less than 7 cm and a smallest sphere placeable in the cavity has a diameter of 0.5 mm; and a hard coating on the inner surface, the hard coating having a hardness between 18 to 100 GPa, the hard coating distributed on the inner surface such that a ratio of a coating thickness at a first region of the hard coating to that at a second region of the hard coating ranges from 0.75 to 1.33.

A heterogeneous composition is disclosed, including an alloy mixture and a ceramic additive. The alloy mixture includes a first alloy having a first melting point of at least a first threshold temperature, and a second alloy having a second melting point of less than a second threshold temperature. The second threshold temperature is lower than the first threshold temperature. The first alloy, the second alloy, and the ceramic additive are intermixed with one another as distinct phases. An article is disclosed including a first portion including a material composition, and a second portion including the heterogeneous composition. A method for forming the article is disclosing, including applying the second portion to the first portion.

A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

The present disclosure relates to a first seal for an aircraft blade outer air seal (BOAS) comprising a first portion comprising a first channel and a second channel, and a second portion comprising a first projection and a second projection, wherein the first projection slidably couples to the first channel and the second projection slidably couples to the second channel. The first portion and/or the second portion may be coated with a low friction substance. The first portion may be coupled to a vane support and/or a BOAS, and the second portion may be coupled to a first OAS support. The first seal may enable a radial translation of the BOAS in response to an aircraft maneuver.

The present invention relates to a coating formulation comprising at least one carbonaceous material and a coating material. The present invention also relates to a method for preparing a coating formulation comprising at least one carbonaceous material and a coating material comprising the step of dispersing the at least one carbonaceous material in the coating material.

A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

An erosion and corrosion resistant protective coating for turbomachinery application includes at least one ceramic or metal-ceramic coating segment deposited on surface of a conductive metal substrate subjected to a pre-deposition treatment by at least blasting to provide the surface with texture. The erosion and corrosion resistant coating has a plurality of dome-like structures with dome width between in range from about 0.01 m to about 30 m. The at least one coating segment is formed by condensation of ion bombardment from a metal-gaseous plasma flow, wherein, at least during deposition of first micron of the coating segment, deposition rate of metal ions is at least 3 m/hr and kinetic energy of deposited metal ions exceeds 5 eV.

A coating consists essentially of one or more selected from the group of nitrides of one or more first metals of titanium, zirconium and hafnium beyond 0 at % but less than 100 at % and a balance of silicon, and nitrides of one or more second metals of vanadium, niobium and tantalum.